Flying-machine.



W. H. STEBBINS & L. GEYNET.

FLYING MACHINE.

APPLICATION FILED OCT. 20, 1910.

1,000,127, Q Patented Aug. 8,1911.

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ATTORNE Y m STATES PATENT canton.

WILLIAM H. STEBBI-NS AND LOUIS GEYNET, OF NORWICH, CONNECTICUT.

FLYIN G-MACHIN E.

To" all whom it concern.

Be itknown that we, WILLIAM-H. STEE- have invented certain new and useful Imp'rovements in Flying-Machines, of Which the following is a specification.

This invention-relates to that type of flying machines now commonly referred to as aeroplanes and our immediate objectis to provide simple but effective means for controlling and preserving the balance, or horizontal position of such aeroplanes.

Briefly described our said improvement consists of one or more blades that are normally in parallel relation to the vplanes proper; said blade or blades being however capable of torsional adjustment with respect to the planes and to each other in order to overcome and counteract any tendency on the part of the planes to drive or glide in undesirable or dangerous directions.

In order to explain our invention clearly we have provided the accompanying drawings, in which I Figure '1 is a perspective view of an aeroplane embodying our present improvements, as it appears when in flight, and when viewed from below. Fig. 2 is a relatively reduced, side, elevation, Fig. 3 a front or head-on el'evation,'and Fig. 4 a top or plan view of the same. In- Fig. 5 we have shown, detached, novel mechanism by means of which we are able to control, conveniently and positively, the steering and balancing devices as we will explain in detail hereinafter.

Referring to these several views, the numerals 10, 11 and12 indicate the planes of our illustrated flying machines, the same be-.

ing arranged in superimposed, parallel, re? lation to each other and suitably spaced apart by means of stays 13. At the rear of the machine is hinged a vertical rudder 14.

At the front'of the machine, preferably in the same plane with the upper plane 10,. is

a rod or shaft 14 that bears at all times a fixed relation to the planes, and upon this rod- 14 are hinged, or journaled, relatively smaller auxiliary planes or balancing blades 15 and-=16 that are adjustable eithensindependently of each other, or in unison. Under ordinary, or normal, conditions these supplemental blades are held in parallel re Specification of letters Patent. Patented Aug, 8, 1911. Application filed October 20, 1910, Serial No. 588,139. i

lation with the main planes 10, 11 and 1 but, 1n the event that the aeroplane, by reason of freaky currents of air, or from other causes, is influenced to depart from its safe position, the blades 15 and 16 (one or both of them) may be brought into use to return the said aeroplane to its normal balance and safe position. For-example, shouldthe aeroplane .dlp to the right, or left, hand. the saldblades may be rocked in'opposite direc tions and so that'the angles of incidence and resistance presented to the atmosphere by, sald blades will tend to force the aeroplane back to its balance and to asafe position.

If it is desired to cause the aeroplane to rise to a greater height, the blades may be tilted in unison and sothat the impact of the atmosphere shall'be against the lower faces of the inclined blades or, if it be desired to glide downward the said blades may be tilted in unison so that the impact of the atmosphere will be against the upper faces of the said blades. The chief value and importance, however. of our described blades, is

in the ease and readiness with which they may be adjusted independently in order to overcome any tendency on the part' of the aeroplaneto lose its lateral equilibrium. We will now describe the novel means whereby we are able to control the adjustment of the.

said balancing blades, and the rudder 14 as well, by a single operating lever. This novel device is shown detached in Fig. 5 of the drawlngs and consists essentially of a lever 17 so mounted that it may be rocked fore and aft, as well as side-wise, or it may be partially rotated, or it can be rocked and rotated simultaneously. The lower end of said lever is swiveled to a short shaft 18 that bears a miter gear 19 which meshes with a similar gear 20, the relative arrangement of the described elements being such that the partial rotation of lever 17 will result in a corresponding rotation of the gear 20. The upper end of lever 17 has secured thereto a hand-wheel 21 that is located within the reach ofthe aviator.

Fixed to the lever 17 is a cross-bar 23-. One end of said cross-bar is connected by a rod 23 with-a short arm 24 that is attached to the blade 16, and the other end of the bar 23 is connected by a rod 23 with an arm 25 that is attached to the blade 15, in such manner that, when the lever 17 is partially rotated, the said blades will be rocked (on however, it is desired to rock the said blades in the same direction, and in unison, it is only necessary for the operator to rock the lever 17 bodily forward or backward, without rotating the said lever; suchrocking movement being made possible by means of the described swivel joint.

Loosely mounted on the lever 17 is a collar 26 havin lateral arms that are connect- .ed by a cor 26 with the tiller let of the rudder 14, insuch mannerthat, when the lever 17 is rocked sidewise, the tiller cord 26 will swing the connected tiller and rudder. It will thus be seen that, by properly manipulating the lever 17, the balancin blades 15-16 may be readily adjusted an the rudder 14: may also be controlled. WVe also, by'preference, connect the short shaft 18 with the fork of the front steering wheel 27 so-that the aeroplane may be steered 'by means of the lever 17 before the said aeroplane leaves the ground.

Instead of'the two blades 15-16 we may substitute therefor a modified form of balancing device, consisting of a single blade.

of flexible material capable of being warped,

bent or deflected at its opposite end port-ions, in which case the rods 23 and 23? and the arms 2%25 would be located at the opposite ends of said blade.

Our described improvements are simple in construction, they may be applied to flying machines, without adding materially to the weight of such machines and they make it possible for the aviator to control the balancing and steering of the machine by means of a single lever.

Having thus described our invention, we claim as new and wish to secure by Letters Patent In a flying-machine, two balancing planes, controlling mechanism therefor, operable either to tilt said planes in the same direction, or in opposite directions, including a rotatable lever movable forward and backward, said lever carrying a cross-bar fast thereon, arms attached to said planes, and rods secured at one end to said arms and at the other end to the ends of said crossbar; a miter-gear opera'tively associated with, and rotatable by the rotation of, said lever, a second miter-gear meshing with said first miter-gear, and a steering-gear operatively associated with, and movable by the actuation of, said second miter-gear.

' WILLIAM H. STEBBINS.

LOUIS GEYNET.

Witnesses:

' FRANK O. PALMER,

MADELIrIE D. RITCHIE, 

